US20160130948A1 - Rotor for a turbine - Google Patents
Rotor for a turbine Download PDFInfo
- Publication number
- US20160130948A1 US20160130948A1 US14/899,171 US201414899171A US2016130948A1 US 20160130948 A1 US20160130948 A1 US 20160130948A1 US 201414899171 A US201414899171 A US 201414899171A US 2016130948 A1 US2016130948 A1 US 2016130948A1
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- United States
- Prior art keywords
- rotor
- tie rod
- turbine
- groove
- coupling element
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
- F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/025—Fixing blade carrying members on shafts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/026—Shaft to shaft connections
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/10—Anti- vibration means
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/24—Rotors for turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/60—Shafts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
Definitions
- the invention relates to a rotor for a turbine, comprising a number of rotor components arranged in a row in the axial direction and connected by means of a tie rod, wherein in one of the rotor components there is arranged a groove extending in the circumferential direction and open in the axial direction, wherein a coupling element surrounding the tie rod is arranged in the groove to brace the tie rod.
- a turbine is a fluid flow machine, which converts the internal energy (enthalpy) of a flowing fluid (liquid or gas) into rotational energy and ultimately into mechanical drive energy. A proportion of the fluid stream's internal energy is removed therefrom by the maximally eddy-free, laminar flow around the turbine blades and passes to the rotor blades of the turbine. This then sets the turbine shaft in rotation, and the useful power is output to a coupled-on working machine, such as for example a generator.
- the rotor blades and shaft are parts of the mobile turbine rotor or wheel, which is arranged within a housing.
- a plurality of blades are mounted on the shaft.
- Rotor blades mounted in a plane in each case form a blade wheel or impeller.
- the blades have a slightly curved profile, similar to an aircraft wing.
- a stator is conventionally located upstream of each impeller.
- the stator guide vanes protrude from the housing into the flowing medium and cause it to swirl.
- the swirl (kinetic energy) produced in the stator is used in the subsequent impeller to set in rotation the shaft on which the impeller blades are mounted.
- the stator and impeller together are known as a stage. A plurality of such stages are often connected in series.
- the rotor of a turbine is as a rule held together in the axial direction by means of a tie rod.
- the individual rotor components such as turbine wheel disks, rotor disks and hollow shafts are arranged in a row and clamped by a tie rod.
- the rotor disks are here connected together interlockingly by Hirth toothing, such that torque may be transferred between the individual elements.
- the tie rod is in this case held by bracing means which are inserted in the various compressor and turbine wheel disks and in the cooling air separation tube.
- annular, conically bevelled coupling elements are conventionally provided, which engage in a groove introduced into the respective rotor component, said groove extending in the circumferential direction and being open in the axial direction.
- the coupling elements are here heated on assembly, so that they are connected by shrink fit in the groove of the respective rotor component such as for example a wheel disk. Due to the conical shape, the coupling elements enclose the tie rod flush at their smallest diameter and likewise exhibit a shrink fit at this point.
- bracing means an additional axial securing component is typically necessary to prevent any possible axial travel.
- the retaining elements must always be placed between two disks.
- US 2007/0286733 A1 discloses thermal separation of rotor disks and tie rod of a gas turbine. To this end, an insulation ring and two spacer segments inserted from radially outside are arranged between the last rotor disk and the end of the tie rod. To secure the latter against loss caused by centrifugal force, a sleeve is put over the insulation ring and the spacer elements, which sleeve is in turn secured by a split ring against axial displacement.
- a disadvantage here is that the tie rod is not braced between its two ends and is thus capable of oscillating.
- Said object is achieved according to the invention by arranging the coupling element serving in radial bracing of the tie rod relative to the other rotor components on a retaining element connected to the tie rod.
- the invention is here based on the consideration that particularly stable bracing of the tie rod would be possible if fixing of the coupling element, i.e. of the part engaging in the groove in the respective rotor component, were no longer ensured solely by shrinking on and thus via noninterlocking connection to the tie rod itself. Rather, an interlocking connection should be provided instead. This is achievable using technically simple means, if retaining elements connected to the tie rod are provided thereon, the coupling element being arranged on said retaining elements.
- the coupling element is of annular construction. This gives rise to bracing of the tie rod which is particularly simple to produce and assemble. Because the coupling element is arranged on a separate retaining element on the tie rod, a cone shape is also no longer essential; rather, the coupling element may form a ring in the form of a simple cylinder surface.
- the groove in the respective rotor component is advantageously constructed to extend completely around the tie rod.
- the coupling element may lie in the groove over the complete circumference, so improving stability.
- a second circumferentially extending groove open in the axial direction towards the first groove is arranged in the respective retaining element, the coupling element engaging in said second groove.
- the groove in the retaining element is axially opposite the groove in the respective rotor component. The annular coupling element thus engages on a first axial side in the groove in the rotor component, and on the other axial side in the groove in the retaining element.
- a plurality of retaining elements is here arranged over the circumference of the tie rod.
- the number of retaining elements may then be adapted in line with requirements: the more retaining elements are provided, the better is the bracing of the tie rod.
- a smaller number of retaining elements may however be advantageous with regard to weight and complexity of assembly.
- the respective retaining element is a nut screwed together with the tie rod. This further simplifies assembly: for this purpose it is merely necessary to fit threads to the tie rod which project out of the tie rod in the radial direction. Nuts may then be screwed in the above-described form onto these threads, said nuts then acting as retaining elements to retain the coupling elements and thus brace the tie rod.
- coupling element and/or retaining element are fitted in a preheated state. This simplifies assembly. After cooling of the elements, a shrink fit is established, which firmly stabilizes the tie rod.
- a shrink fit is established, which firmly stabilizes the tie rod.
- the groove in the retaining element is displaced towards the axis of the tie rod and thus an offset arises relative to the groove in the respective rotor component.
- pretension thus arises, which counteracts the centrifugal force arising on operation and thus enables particularly stable retention.
- a turbine advantageously comprises a rotor as described.
- the turbine here advantageously takes the form of a gas turbine. It is precisely in gas turbines that the thermal and mechanical loads are particularly high, such that the described configuration of the tie rod bracing offers particular advantages with regard to stability.
- a power plant advantageously comprises such a turbine.
- FIG. 1 shows a partial longitudinal section through a gas turbine
- FIG. 2 is a schematic diagram of tie rod bracing
- FIG. 3 shows a longitudinal section through the tie rod bracing in the region of the grooves.
- FIG. 1 shows a turbine 100 , here a gas turbine, in partial longitudinal section.
- the gas turbine 100 comprises in its interior a rotor 103 which is mounted to rotate about an axis of rotation ( 102 ) (axial direction) and is also known as a turbine wheel.
- the following follow one another along the rotor 103 : an intake housing 104 , a compressor 105 , a toroidal combustion chamber 110 , in particular annular combustion chamber 106 , with a plurality of coaxially arranged burners 107 , a turbine 108 and the waste gas housing 109 .
- the annular combustion chamber 106 communicates with an annular hot gas duct 111 .
- There for example four series-connected turbine stages 112 form the turbine 108 .
- Each turbine stage 112 is formed from two rings of blades and vanes. Viewed in the direction of flow of a working medium 113 , a row 125 formed of rotor blades 120 follows a row of stator guide vanes 115 in the hot gas duct 111 .
- the stator guide vanes 130 are in this case fastened to the stator 143 , whereas the rotor blades 120 of a row 125 are mounted on the rotor 103 by means of a turbine disk 133 .
- the rotor blades 120 thus form constituents of the rotor or turbine wheel 103 .
- a generator or a machine (not shown) is coupled to the rotor 103 .
- air 135 is drawn in by the compressor 105 through the intake housing 104 and compressed.
- the compressed air provided at the turbine-side end of the compressor 105 is guided to the burners 107 and there is mixed with a fuel.
- the mixture is then combusted in the combustion chamber 110 , forming the working medium 113 .
- the working medium 113 flows from there along the hot gas duct 111 past the stator guide vanes 130 and the rotor blades 120 .
- the working medium 113 expands in a pulse-transmitting manner, such that the rotor blades 120 drive the rotor 103 and the latter drives the working machine coupled thereto.
- the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100 .
- the stator guide vanes 130 and rotor blades 120 of the turbine stage 112 which comes first when viewed in the direction of flow of the working medium 113 are subject to the most thermal load. To withstand the temperatures prevailing there, these are cooled by means of a coolant.
- Each stator guide vane 130 comprises a guide vane root (not shown here) facing the inner housing 138 of the turbine 108 and a guide vane tip opposite the guide vane root.
- the guide vane tip faces the rotor 103 and is fixed to a sealing ring 140 of the stator 143 .
- Each sealing ring 140 here surrounds the shaft of the rotor 103 .
- the turbine disks 130 and further components not described in any greater detail, such as hollow shafts, are connected to the rotor 103 via a tie rod 144 . To prevent oscillation of the tie rod 144 , the latter is braced on the rotor components, as illustrated in the schematic diagram in FIG. 2 .
- FIG. 2 shows a longitudinal section (relative to the axis 102 ) through the tie rod 144 at the radial outer edge thereof.
- a thread 146 Introduced into the tie rod 144 is a thread 146 which projects radially out of the tie rod 144 .
- a nut 148 is screwed onto the thread 146 as a retaining element. Similar combinations of thread 146 and nut 148 are arranged at regular intervals over the circumference of the tie rod 144 .
- the nut 148 comprises a groove 150 , which is open in the axial direction and faces the turbine disk 130 . Opposite the groove 150 a further groove 152 is introduced into the turbine disk 130 , extending around the entire circumference.
- An annular coupling element is arranged in the two grooves 150 , 152 in the manner of a tongue and groove joint and thereby fixes the tie rod 144 in the radial direction. In the axial direction the turbine disk 130 is fixed by way of the tension of the tie rod 144 , while the nut 148 is fixed via the thread 146 .
- Corresponding bracing means may be provided on each rotor component in different axial regions of the tie rod 144 .
- the nut 148 comprises a central opening 156 passing through it in the axial direction. Cooling air may pass through this opening 156 , as between the individual nuts 148 , so enabling internal cool air conduction for cooling the tie rod 144 .
- FIG. 3 shows a detail of a longitudinal section of the region around the coupling element 154 .
- the nut 148 here additionally comprises a projection 158 which rests against the turbine disk 130 and brings about stabilization in the axial direction.
- nut 148 and coupling element 154 are heated. On cooling, nut 148 and coupling element 154 therefore shrink, such that the coupling element 154 and groove 150 are moved towards the axis 102 . In this way, the coupling element 154 rests on the radial inner side of the groove 152 in the turbine disk 130 and on the radial outer side of the groove 150 in the nut 148 . This results in pretension, which counteracts the centrifugal force arising during operation.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- This application is the U.S. National Stage of International Application No. PCT/EP2014/063812 filed Jun 30, 2014, and claims the benefit thereof. The International Application claims the benefit of German Application No. DE 102013213115.1 filed Jul 4, 2013. All of the applications are incorporated by reference herein in their entirety.
- The invention relates to a rotor for a turbine, comprising a number of rotor components arranged in a row in the axial direction and connected by means of a tie rod, wherein in one of the rotor components there is arranged a groove extending in the circumferential direction and open in the axial direction, wherein a coupling element surrounding the tie rod is arranged in the groove to brace the tie rod.
- A turbine is a fluid flow machine, which converts the internal energy (enthalpy) of a flowing fluid (liquid or gas) into rotational energy and ultimately into mechanical drive energy. A proportion of the fluid stream's internal energy is removed therefrom by the maximally eddy-free, laminar flow around the turbine blades and passes to the rotor blades of the turbine. This then sets the turbine shaft in rotation, and the useful power is output to a coupled-on working machine, such as for example a generator. The rotor blades and shaft are parts of the mobile turbine rotor or wheel, which is arranged within a housing.
- As a rule, a plurality of blades are mounted on the shaft. Rotor blades mounted in a plane in each case form a blade wheel or impeller. The blades have a slightly curved profile, similar to an aircraft wing. A stator is conventionally located upstream of each impeller. The stator guide vanes protrude from the housing into the flowing medium and cause it to swirl. The swirl (kinetic energy) produced in the stator is used in the subsequent impeller to set in rotation the shaft on which the impeller blades are mounted. The stator and impeller together are known as a stage. A plurality of such stages are often connected in series.
- The rotor of a turbine is as a rule held together in the axial direction by means of a tie rod. The individual rotor components such as turbine wheel disks, rotor disks and hollow shafts are arranged in a row and clamped by a tie rod. The rotor disks are here connected together interlockingly by Hirth toothing, such that torque may be transferred between the individual elements.
- To reduce oscillation of the tie rod, the tie rod is in this case held by bracing means which are inserted in the various compressor and turbine wheel disks and in the cooling air separation tube. To this end, annular, conically bevelled coupling elements are conventionally provided, which engage in a groove introduced into the respective rotor component, said groove extending in the circumferential direction and being open in the axial direction. The coupling elements are here heated on assembly, so that they are connected by shrink fit in the groove of the respective rotor component such as for example a wheel disk. Due to the conical shape, the coupling elements enclose the tie rod flush at their smallest diameter and likewise exhibit a shrink fit at this point.
- However, with the known bracing means an additional axial securing component is typically necessary to prevent any possible axial travel. For example, the retaining elements must always be placed between two disks. Despite these measures, the risk of a temporary, transient loss of contact still exists.
- It is moreover known from DE 2 135 088 A1 to secure the tie rod of a rotor of a fluid flow machine relative to an outer casing by way of a circumferentially toothed pair of bushes.
- In addition, US 2007/0286733 A1 discloses thermal separation of rotor disks and tie rod of a gas turbine. To this end, an insulation ring and two spacer segments inserted from radially outside are arranged between the last rotor disk and the end of the tie rod. To secure the latter against loss caused by centrifugal force, a sleeve is put over the insulation ring and the spacer elements, which sleeve is in turn secured by a split ring against axial displacement. A disadvantage here is that the tie rod is not braced between its two ends and is thus capable of oscillating.
- It is therefore an object of the invention to provide a rotor of the above-stated type which uses technically simple means to achieve particularly stable bracing of the tie rod to prevent oscillations.
- Said object is achieved according to the invention by arranging the coupling element serving in radial bracing of the tie rod relative to the other rotor components on a retaining element connected to the tie rod.
- The invention is here based on the consideration that particularly stable bracing of the tie rod would be possible if fixing of the coupling element, i.e. of the part engaging in the groove in the respective rotor component, were no longer ensured solely by shrinking on and thus via noninterlocking connection to the tie rod itself. Rather, an interlocking connection should be provided instead. This is achievable using technically simple means, if retaining elements connected to the tie rod are provided thereon, the coupling element being arranged on said retaining elements.
- In one advantageous configuration, the coupling element is of annular construction. This gives rise to bracing of the tie rod which is particularly simple to produce and assemble. Because the coupling element is arranged on a separate retaining element on the tie rod, a cone shape is also no longer essential; rather, the coupling element may form a ring in the form of a simple cylinder surface.
- The groove in the respective rotor component is advantageously constructed to extend completely around the tie rod. Thus, if the coupling element has a simple annular shape it may lie in the groove over the complete circumference, so improving stability.
- In a further advantageous configuration, a second circumferentially extending groove open in the axial direction towards the first groove is arranged in the respective retaining element, the coupling element engaging in said second groove. In other words: the groove in the retaining element is axially opposite the groove in the respective rotor component. The annular coupling element thus engages on a first axial side in the groove in the rotor component, and on the other axial side in the groove in the retaining element.
- Advantageously, a plurality of retaining elements is here arranged over the circumference of the tie rod. The number of retaining elements may then be adapted in line with requirements: the more retaining elements are provided, the better is the bracing of the tie rod. A smaller number of retaining elements may however be advantageous with regard to weight and complexity of assembly.
- In a particularly simple advantageous configuration, the respective retaining element is a nut screwed together with the tie rod. This further simplifies assembly: for this purpose it is merely necessary to fit threads to the tie rod which project out of the tie rod in the radial direction. Nuts may then be screwed in the above-described form onto these threads, said nuts then acting as retaining elements to retain the coupling elements and thus brace the tie rod.
- In a method for producing a rotor as described, coupling element and/or retaining element are fitted in a preheated state. This simplifies assembly. After cooling of the elements, a shrink fit is established, which firmly stabilizes the tie rod. Of particular advantage is the fact that, on shrinkage, the groove in the retaining element is displaced towards the axis of the tie rod and thus an offset arises relative to the groove in the respective rotor component. In conjunction with the reduction on cooling of the diameter of the coupling element, pretension thus arises, which counteracts the centrifugal force arising on operation and thus enables particularly stable retention.
- A turbine advantageously comprises a rotor as described.
- The turbine here advantageously takes the form of a gas turbine. It is precisely in gas turbines that the thermal and mechanical loads are particularly high, such that the described configuration of the tie rod bracing offers particular advantages with regard to stability.
- A power plant advantageously comprises such a turbine.
- The advantages achieved with the invention consist in particular in that, by bracing the tie rod not by shrinking the coupling element onto the tie rod itself, but rather by securing to a separate retaining element on the tie rod, oscillation of the tie rod can be prevented in a particularly stable and technically simple manner. In addition, internal supply of cooling air is enabled in combination with bracing of the tie rod, since passages remain between the retaining elements. Tie rod bracing is achieved without any need for additional axial securing components. The risk of a temporary, transient loss of contact is eliminated.
- An exemplary embodiment of the invention is explained in greater detail below with reference to drawings, in which:
-
FIG. 1 shows a partial longitudinal section through a gas turbine, -
FIG. 2 is a schematic diagram of tie rod bracing, and -
FIG. 3 shows a longitudinal section through the tie rod bracing in the region of the grooves. - Identical parts are provided with the same reference numerals in all the figures.
-
FIG. 1 shows aturbine 100, here a gas turbine, in partial longitudinal section. Thegas turbine 100 comprises in its interior arotor 103 which is mounted to rotate about an axis of rotation (102) (axial direction) and is also known as a turbine wheel. The following follow one another along the rotor 103: anintake housing 104, acompressor 105, atoroidal combustion chamber 110, in particularannular combustion chamber 106, with a plurality of coaxially arrangedburners 107, aturbine 108 and thewaste gas housing 109. Theannular combustion chamber 106 communicates with an annularhot gas duct 111. There for example four series-connected turbine stages 112 form theturbine 108. Eachturbine stage 112 is formed from two rings of blades and vanes. Viewed in the direction of flow of a workingmedium 113, arow 125 formed ofrotor blades 120 follows a row ofstator guide vanes 115 in thehot gas duct 111. Thestator guide vanes 130 are in this case fastened to thestator 143, whereas therotor blades 120 of arow 125 are mounted on therotor 103 by means of aturbine disk 133. Therotor blades 120 thus form constituents of the rotor orturbine wheel 103. A generator or a machine (not shown) is coupled to therotor 103. During operation of thegas turbine 100,air 135 is drawn in by thecompressor 105 through theintake housing 104 and compressed. The compressed air provided at the turbine-side end of thecompressor 105 is guided to theburners 107 and there is mixed with a fuel. The mixture is then combusted in thecombustion chamber 110, forming the workingmedium 113. The workingmedium 113 flows from there along thehot gas duct 111 past thestator guide vanes 130 and therotor blades 120. At therotor blades 120 the workingmedium 113 expands in a pulse-transmitting manner, such that therotor blades 120 drive therotor 103 and the latter drives the working machine coupled thereto. - The components exposed to the hot working
medium 113 are subject to thermal loads during operation of thegas turbine 100. Along with the heat shield bricks lining theannular combustion chamber 106, thestator guide vanes 130 androtor blades 120 of theturbine stage 112 which comes first when viewed in the direction of flow of the workingmedium 113 are subject to the most thermal load. To withstand the temperatures prevailing there, these are cooled by means of a coolant. Likewise, the blades andvanes - Each
stator guide vane 130 comprises a guide vane root (not shown here) facing theinner housing 138 of theturbine 108 and a guide vane tip opposite the guide vane root. The guide vane tip faces therotor 103 and is fixed to asealing ring 140 of thestator 143. Each sealingring 140 here surrounds the shaft of therotor 103. Theturbine disks 130, and further components not described in any greater detail, such as hollow shafts, are connected to therotor 103 via atie rod 144. To prevent oscillation of thetie rod 144, the latter is braced on the rotor components, as illustrated in the schematic diagram inFIG. 2 . -
FIG. 2 shows a longitudinal section (relative to the axis 102) through thetie rod 144 at the radial outer edge thereof. Introduced into thetie rod 144 is athread 146 which projects radially out of thetie rod 144. Anut 148 is screwed onto thethread 146 as a retaining element. Similar combinations ofthread 146 andnut 148 are arranged at regular intervals over the circumference of thetie rod 144. - The
nut 148 comprises agroove 150, which is open in the axial direction and faces theturbine disk 130. Opposite the groove 150 afurther groove 152 is introduced into theturbine disk 130, extending around the entire circumference. An annular coupling element is arranged in the twogrooves tie rod 144 in the radial direction. In the axial direction theturbine disk 130 is fixed by way of the tension of thetie rod 144, while thenut 148 is fixed via thethread 146. Corresponding bracing means may be provided on each rotor component in different axial regions of thetie rod 144. Thenut 148 comprises acentral opening 156 passing through it in the axial direction. Cooling air may pass through thisopening 156, as between theindividual nuts 148, so enabling internal cool air conduction for cooling thetie rod 144. -
FIG. 3 shows a detail of a longitudinal section of the region around thecoupling element 154. Thenut 148 here additionally comprises aprojection 158 which rests against theturbine disk 130 and brings about stabilization in the axial direction. - During assembly,
nut 148 andcoupling element 154 are heated. On cooling,nut 148 andcoupling element 154 therefore shrink, such that thecoupling element 154 and groove 150 are moved towards theaxis 102. In this way, thecoupling element 154 rests on the radial inner side of thegroove 152 in theturbine disk 130 and on the radial outer side of thegroove 150 in thenut 148. This results in pretension, which counteracts the centrifugal force arising during operation.
Claims (11)
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
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DE102013213115.1 | 2013-07-04 | ||
DE102013213115 | 2013-07-04 | ||
DE102013213115.1A DE102013213115A1 (en) | 2013-07-04 | 2013-07-04 | Rotor for a turbine |
PCT/EP2014/063812 WO2015000830A2 (en) | 2013-07-04 | 2014-06-30 | Rotor for a turbine |
Publications (2)
Publication Number | Publication Date |
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US20160130948A1 true US20160130948A1 (en) | 2016-05-12 |
US10174618B2 US10174618B2 (en) | 2019-01-08 |
Family
ID=51062810
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/899,171 Expired - Fee Related US10174618B2 (en) | 2013-07-04 | 2014-06-30 | Rotor for a turbine |
Country Status (6)
Country | Link |
---|---|
US (1) | US10174618B2 (en) |
EP (1) | EP3017147B1 (en) |
JP (1) | JP2016524082A (en) |
CN (1) | CN105358797A (en) |
DE (1) | DE102013213115A1 (en) |
WO (1) | WO2015000830A2 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
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US12037926B2 (en) | 2016-02-05 | 2024-07-16 | Siemens Energy Global GmbH & Co. KG | Rotor comprising a rotor component arranged between two rotor discs |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3293354B1 (en) * | 2016-09-07 | 2021-04-14 | Ansaldo Energia IP UK Limited | Turboengine blading member and a method for assembling such a member |
KR101967067B1 (en) * | 2017-10-27 | 2019-04-09 | 두산중공업 주식회사 | Torque tube and gas turbine comprising it |
EP4013950B1 (en) * | 2019-10-18 | 2023-11-08 | Siemens Energy Global GmbH & Co. KG | Rotor comprising a rotor component arranged between two rotor discs |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
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GB858763A (en) * | 1957-06-14 | 1961-01-18 | Napier & Son Ltd | Rotors for multi-stage axial flow compressors or turbines |
DE2643886C2 (en) | 1976-09-29 | 1978-02-09 | Kraftwerk Union AG, 4330 Mülheim | Disc-type gas turbine rotor |
JPS5939903A (en) * | 1982-08-30 | 1984-03-05 | Toshiba Corp | Steam turbine rotor |
US5537814A (en) | 1994-09-28 | 1996-07-23 | General Electric Company | High pressure gas generator rotor tie rod system for gas turbine engine |
JP2941698B2 (en) * | 1995-11-10 | 1999-08-25 | 三菱重工業株式会社 | Gas turbine rotor |
JP3636336B2 (en) | 1996-05-28 | 2005-04-06 | 富士電機システムズ株式会社 | Axial exhaust turbine |
DE19821889B4 (en) | 1998-05-15 | 2008-03-27 | Alstom | Method and device for carrying out repair and / or maintenance work in the inner housing of a multi-shell turbomachine |
JP4007062B2 (en) | 2002-05-22 | 2007-11-14 | 株式会社日立製作所 | Gas turbine and gas turbine power generator |
US7470115B2 (en) | 2004-07-13 | 2008-12-30 | Honeywell International Inc. | Outer diameter nut piloting for improved rotor balance |
US7452188B2 (en) * | 2005-09-26 | 2008-11-18 | Pratt & Whitney Canada Corp. | Pre-stretched tie-bolt for use in a gas turbine engine and method |
WO2008012195A1 (en) | 2006-07-24 | 2008-01-31 | Siemens Aktiengesellschaft | Method for unscrewing a ring half of a guidance apparatus, which is annular overall, from a lower housing half of a stationary flow machine though which flow can pass axially, mounting apparatus, mounting apparatus assembly and auxiliary half-ring for this purpose |
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US8650885B2 (en) | 2009-12-22 | 2014-02-18 | United Technologies Corporation | Retaining member for use with gas turbine engine shaft and method of assembly |
ITMI20101918A1 (en) | 2010-10-20 | 2012-04-21 | Ansaldo Energia Spa | GAS TURBINE PLANT FOR THE PRODUCTION OF ELECTRIC ENERGY, EQUIPPED WITH AN EQUIPMENT FOR MONITORING OF ROTATING PARTS |
EP2565387A1 (en) * | 2011-08-29 | 2013-03-06 | Siemens Aktiengesellschaft | Flow engine with a contactless temperature sensor |
-
2013
- 2013-07-04 DE DE102013213115.1A patent/DE102013213115A1/en not_active Ceased
-
2014
- 2014-06-30 JP JP2016522557A patent/JP2016524082A/en active Pending
- 2014-06-30 CN CN201480038127.0A patent/CN105358797A/en active Pending
- 2014-06-30 WO PCT/EP2014/063812 patent/WO2015000830A2/en active Application Filing
- 2014-06-30 US US14/899,171 patent/US10174618B2/en not_active Expired - Fee Related
- 2014-06-30 EP EP14734797.5A patent/EP3017147B1/en not_active Not-in-force
Patent Citations (1)
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US3680979A (en) * | 1970-10-07 | 1972-08-01 | Carrier Corp | Rotor structure for turbo machines |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US12037926B2 (en) | 2016-02-05 | 2024-07-16 | Siemens Energy Global GmbH & Co. KG | Rotor comprising a rotor component arranged between two rotor discs |
Also Published As
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JP2016524082A (en) | 2016-08-12 |
EP3017147A2 (en) | 2016-05-11 |
CN105358797A (en) | 2016-02-24 |
EP3017147B1 (en) | 2017-04-12 |
WO2015000830A2 (en) | 2015-01-08 |
WO2015000830A3 (en) | 2015-02-26 |
US10174618B2 (en) | 2019-01-08 |
DE102013213115A1 (en) | 2015-01-22 |
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